BE1028335B1 - Low pressure compressor sub-assembly of an aircraft turbomachine - Google Patents

Low pressure compressor sub-assembly of an aircraft turbomachine

Info

Publication number
BE1028335B1
BE1028335B1 BE20205357A BE202005357A BE1028335B1 BE 1028335 B1 BE1028335 B1 BE 1028335B1 BE 20205357 A BE20205357 A BE 20205357A BE 202005357 A BE202005357 A BE 202005357A BE 1028335 B1 BE1028335 B1 BE 1028335B1
Authority
BE
Belgium
Prior art keywords
pressure compressor
assembly
low pressure
aircraft turbomachine
compressor sub
Prior art date
Application number
BE20205357A
Other languages
French (fr)
Other versions
BE1028335A1 (en
Inventor
Stéphane Hiernaux
Original Assignee
Safran Aero Boosters
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aero Boosters filed Critical Safran Aero Boosters
Priority to BE20205357A priority Critical patent/BE1028335B1/en
Priority to CN202180045164.4A priority patent/CN115720609A/en
Priority to EP21725160.2A priority patent/EP4153867A1/en
Priority to US17/999,261 priority patent/US11898468B2/en
Priority to PCT/EP2021/062437 priority patent/WO2021233730A1/en
Publication of BE1028335A1 publication Critical patent/BE1028335A1/en
Application granted granted Critical
Publication of BE1028335B1 publication Critical patent/BE1028335B1/en
Priority to US18/537,319 priority patent/US20240229659A9/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/663—Sound attenuation
    • F04D29/665—Sound attenuation by means of resonance chambers or interference
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • F05D2220/3217—Application in turbines in gas turbines for a special turbine stage for a special compressor stage for the first stage of a compressor or a low pressure compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L’invention concerne un sous-ensemble (1) de compresseur basse pression (120) d’une turbomachine d’aéronef (100) comprenant un redresseur (121) muni d’aubes (7) en porte-à-faux et un moyeu (6) de rotor comprenant une cavité (2) couverte par une virole intérieure (3) en vis-à-vis des aubes (7), des orifices (5) étant pratiqués dans cette virole intérieure (3) pour permettre la circulation d’un flux d’air d’aval en amont du compresseur basse pression (120).The invention relates to a sub-assembly (1) of a low-pressure compressor (120) of an aircraft turbine engine (100) comprising a stator (121) provided with cantilevered blades (7) and a hub (6) rotor comprising a cavity (2) covered by an inner shroud (3) vis-à-vis the blades (7), orifices (5) being made in this inner shroud (3) to allow the circulation of a downstream air flow upstream of the low pressure compressor (120).

BE20205357A 2020-05-20 2020-05-20 Low pressure compressor sub-assembly of an aircraft turbomachine BE1028335B1 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
BE20205357A BE1028335B1 (en) 2020-05-20 2020-05-20 Low pressure compressor sub-assembly of an aircraft turbomachine
CN202180045164.4A CN115720609A (en) 2020-05-20 2021-05-11 Subassembly for a low-pressure compressor of an aircraft turbine engine
EP21725160.2A EP4153867A1 (en) 2020-05-20 2021-05-11 Sub-assembly for a low-pressure compressor of an aircraft turbine engine
US17/999,261 US11898468B2 (en) 2020-05-20 2021-05-11 Sub-assembly for a low-pressure compressor of an aircraft turbine engine
PCT/EP2021/062437 WO2021233730A1 (en) 2020-05-20 2021-05-11 Sub-assembly for a low-pressure compressor of an aircraft turbine engine
US18/537,319 US20240229659A9 (en) 2020-05-20 2023-12-12 Sub-assembly for a low-pressure compressor of an aircraft turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
BE20205357A BE1028335B1 (en) 2020-05-20 2020-05-20 Low pressure compressor sub-assembly of an aircraft turbomachine

Publications (2)

Publication Number Publication Date
BE1028335A1 BE1028335A1 (en) 2021-12-17
BE1028335B1 true BE1028335B1 (en) 2021-12-20

Family

ID=70968683

Family Applications (1)

Application Number Title Priority Date Filing Date
BE20205357A BE1028335B1 (en) 2020-05-20 2020-05-20 Low pressure compressor sub-assembly of an aircraft turbomachine

Country Status (5)

Country Link
US (2) US11898468B2 (en)
EP (1) EP4153867A1 (en)
CN (1) CN115720609A (en)
BE (1) BE1028335B1 (en)
WO (1) WO2021233730A1 (en)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6514039B1 (en) * 1999-11-25 2003-02-04 Rolls-Royce Plc Processing tip treatment bars in a gas turbine engine
US20050249578A1 (en) * 2004-05-07 2005-11-10 Leblanc Andre D Shockwave-induced boundary layer bleed
US20100034637A1 (en) * 2008-08-08 2010-02-11 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine
EP2434163A1 (en) * 2010-09-24 2012-03-28 Siemens Aktiengesellschaft Compressor

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE69204861T2 (en) * 1991-01-30 1996-05-23 United Technologies Corp Fan housing with recirculation channels.
FR2846034B1 (en) * 2002-10-22 2006-06-23 Snecma Moteurs CARTER, COMPRESSOR, TURBINE AND COMBUSTION TURBOMOTOR COMPRISING SUCH A CARTER
DE102008011644A1 (en) * 2008-02-28 2009-09-03 Rolls-Royce Deutschland Ltd & Co Kg Housing structuring for axial compressor in the hub area
GB201318036D0 (en) * 2013-10-11 2013-11-27 Rolls Royce Plc Tip treatment bars in a turbine engine
EP2987956A1 (en) * 2014-08-18 2016-02-24 Siemens Aktiengesellschaft Compressor aerofoil
BE1023134B1 (en) 2015-05-27 2016-11-29 Techspace Aero S.A. DAWN AND VIROLE WITH COMPRESSOR OF AXIAL TURBOMACHINE COMPRESSOR
US11203939B2 (en) * 2018-12-12 2021-12-21 Raytheon Technologies Corporation Airfoil platform with cooling orifices

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6514039B1 (en) * 1999-11-25 2003-02-04 Rolls-Royce Plc Processing tip treatment bars in a gas turbine engine
US20050249578A1 (en) * 2004-05-07 2005-11-10 Leblanc Andre D Shockwave-induced boundary layer bleed
US20100034637A1 (en) * 2008-08-08 2010-02-11 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine
EP2434163A1 (en) * 2010-09-24 2012-03-28 Siemens Aktiengesellschaft Compressor

Also Published As

Publication number Publication date
EP4153867A1 (en) 2023-03-29
US11898468B2 (en) 2024-02-13
US20240229659A9 (en) 2024-07-11
CN115720609A (en) 2023-02-28
US20230184121A1 (en) 2023-06-15
WO2021233730A1 (en) 2021-11-25
BE1028335A1 (en) 2021-12-17
US20240133304A1 (en) 2024-04-25

Similar Documents

Publication Publication Date Title
US8087249B2 (en) Turbine cooling air from a centrifugal compressor
US8147178B2 (en) Centrifugal compressor forward thrust and turbine cooling apparatus
US9726032B2 (en) Gas turbine engine diffuser system for a high pressure (HP) compressor
US20170248155A1 (en) Centrifugal compressor diffuser passage boundary layer control
JP6145296B2 (en) Turbomachine blade tip shroud with parallel casing configuration
EP2080876A3 (en) A turbomachine system and turbine therefor
EP3714144B1 (en) Method of designing a turbine
US10330121B2 (en) Systems and methods for axial compressor with secondary flow
JP2017106452A (en) Gas turbine engine with fillet film holes
US20220356805A1 (en) Airfoil assembly with a fluid circuit
JP2019007478A (en) Rotor blade tip
RU2573094C2 (en) Gas turbine engine
US10240461B2 (en) Stator rim for a turbine engine
US10100841B2 (en) Centrifugal compressor and system
BE1028335B1 (en) Low pressure compressor sub-assembly of an aircraft turbomachine
US20080072566A1 (en) Bleed holes oriented with gaspath and flared for noise reduction
CN111271131B (en) Rotor assembly thermal attenuation structures and systems
RU2538985C1 (en) High-temperature turbine stator
CN108691658B (en) Turbine engine with platform cooling circuit
JPWO2016027834A1 (en) gas turbine
EP2672122A2 (en) Method for controlling temperature of a turbine engine compressor and compressor of a turbine engine
US10626796B2 (en) Film cooling passage with multidimensional diffusion
RU186988U9 (en) CENTRIFUGAL COMPRESSOR DIFFUSER
RU132508U1 (en) COMPRESSOR OF THE GAS TURBINE ENGINE
RU130633U1 (en) TURBINE DRIVER COOLING DEVICE

Legal Events

Date Code Title Description
FG Patent granted

Effective date: 20211220